Electric Jet Engine

Abstract

Electric engine to provide thrust to fly an aircraft. Engine includes housing, air inlet, shaft, bladed rotor having a plurality of magnets secured on shaft, stator having plurality of coils positioned so as to interact with plurality of magnets and an exhaust nozzle. Powering coils causes interaction with magnets that results in bladed rotor rotating and pressurizing and accelerating air received via air inlet and expelling via exhaust nozzle to provide thrust. Engine may include generator having stator with coils secured to shaft via bearings and plurality of rotors with magnets secured to shaft to rotate with shaft. Magnets rotating past coils results in electric generation. Second hollow shaft may be mounted to shaft with bearings and generator may be located with hollow shaft. Second bladed rotor may be connected to, and rotate, second shaft. Engine may include ducts external to bladed rotor and fan to route air therein.

1 . An electric jet engine comprising:
 an engine housing;   an air inlet;   a first stator housing connected to the engine housing, wherein the first stator housing includes at least one first stator core;   a first shaft;   a low-pressure turbine including
 at least one first bladed rotor secured on the first shaft, wherein the at least one first bladed rotor includes a first plurality of blades; 
 a first plurality of magnets mounted on the at least one first bladed rotor; and 
 a first plurality of coils mounted on the at least one first stator core, wherein the first plurality of coils are configured to interact with the first plurality of magnets, wherein the interaction between the first plurality of coils and the first plurality of magnets causes the at least one first bladed rotor to rotate in order to pressurize and accelerate air received via the air inlet, and wherein the rotation of the at least one first bladed rotor causes the first shaft to rotate; 
   a generator including
 a second stator housing secured to the first shaft via first bearings, wherein the second stator housing includes at least one second stator core; 
 at least one rotor secured on the first shaft, wherein the at least one rotor rotates with the rotation of the first shaft; 
 a second plurality of magnets mounted on the at least one rotor; and 
 a second plurality of coils mounted on the at least one second stator core, wherein the second plurality of coils are configured to interact with the second plurality of magnets, wherein the interaction between the second plurality of coils and the second plurality of magnets causes current to flow in the second plurality of coils; 
   a second shaft secured to the second stator housing via second bearings, wherein the second shaft is concentric to the first shaft, and wherein the generator is located within the second stator housing;   a high-pressure turbine including
 at least one second bladed rotor secured to the second shaft via third bearings, wherein the at least one second bladed rotor includes a second plurality of blades; 
 a third plurality of magnets mounted on the at least one second bladed rotor; and 
 a third plurality of coils mounted on the at least one first stator core, wherein the third plurality of coils are configured to interact with the third plurality of magnets, wherein the interaction between the third plurality of coils and the third plurality of magnets causes the at least one second bladed rotor to rotate in order to increase the pressure of the air provided from the low-pressure turbine; and 
   an exhaust nozzle to expel the pressurized air from the high-pressure turbine to provide thrust.   
     
     
         2 . The electric jet engine of  claim 1 , further comprising a power source to power the first and the third plurality of coils. 
     
     
         3 . The electric jet engine of  claim 1 , further comprising a controller to control operation of the first and the third plurality of coils. 
     
     
         4 . The electric jet engine of  claim 1 , further comprising
 ducts formed between the stator housing and the engine housing; and   a ducted fan within the air inlet to route some of the air received via the air inlet to the ducts, wherein rotation of the duct fan is supplied by rotation of the first shaft.   
     
     
         5 . The electric motor of  claim 1 , further comprising a combustion chamber. 
     
     
         6 . The electric motor of  claim 1 , wherein the at least one first bladed rotor includes a first opening to receive the first shaft, a first inner ring surrounding the first opening, and a first outer ring, wherein the first plurality of blades extend from the first inner ring to the first outer ring. 
     
     
         7 . The electric motor of  claim 6 , wherein the first plurality of magnets are located on the first outer ring. 
     
     
         8 . The electric motor of  claim 1 , wherein the at least one second bladed rotor includes a second opening to receive the second shaft, a second inner ring surrounding the second opening, and a second outer ring, wherein the second plurality of blades extend from the second inner ring to the second outer ring. 
     
     
         9 . The electric motor of  claim 8 , wherein the third plurality of magnets are located on the second outer ring. 
     
     
         10 . The electric motor of  claim 1 , utilized in an aircraft. 
     
     
         11 . An electric jet engine comprising:
 an engine housing;   an air inlet;   a first stator housing connected to the engine housing, wherein the first stator housing includes at least two first stator cores;   ducts formed between the first stator housing and the engine housing;   a first shaft;   a second shaft concentric to the first shaft;   at least one first bladed rotor secured on the first shaft, wherein the at least one first bladed rotor includes a first plurality of blades, and wherein the first bladed rotor is to act as a low-pressure turbine;   at least one second bladed rotor secured on the second shaft, wherein the at least one second bladed rotor includes a second plurality of blades and wherein the at least one second bladed rotor is to act as a high-pressure turbine;   a first plurality of magnets mounted on the at least one first bladed rotor;   a second plurality of magnets mounted on the at least one second bladed rotor;   a first plurality of coils mounted on a first of the at least two first stator cores, wherein the first plurality of coils are configured to interact with the first plurality of magnets, wherein the interaction between the first plurality of coils and the first plurality of magnets causes the at least one first bladed rotor to rotate in order to pressurize air received via the air inlet, and wherein the rotation of the at least one first bladed rotor causes the first shaft to rotate;   a second plurality of coils mounted on a second of the at least two first stator cores, wherein the second plurality of coils are configured to interact with the second plurality of magnets, wherein the interaction between the second plurality of coils and the second plurality of magnets causes the at least one second bladed rotor to rotate in order to accelerate the pressurized air;   a generator mounted to the first shaft and located within the second shaft, wherein the generator utilizes the rotation of the first shaft to generate electricity; and   an exhaust nozzle to expel the pressurized and accelerated air to provide thrust.   
     
     
         12 . The electric jet engine of  claim 11 , wherein the generator includes
 a second stator housing secured to the first shaft via first bearings, wherein the second stator housing includes at least one second stator core;   at least one rotor secured on the first shaft, wherein the at least one rotor rotates with the rotation of the first shaft;   a third plurality of magnets mounted on the at least one rotor; and   a third plurality of coils mounted on the at least one second stator core, wherein the third plurality of coils are configured to interact with the third plurality of magnets, wherein the interaction between the third plurality of coils and the third plurality of magnets causes current to flow in the third plurality of coils.   
     
     
         13 . The electric jet engine of  claim 12 , wherein the second shaft is secured to the second stator housing via second bearings. 
     
     
         14 . The electric motor of  claim 11 , further comprising a combustion chamber. 
     
     
         15 . The electric motor of  claim 11 , wherein the at least one first bladed rotor includes a first opening to receive the first shaft, a first inner ring surrounding the first opening, and a first outer ring, wherein the first plurality of blades extend from the first inner ring to the first outer ring. 
     
     
         16 . The electric motor of  claim 15 , wherein the first plurality of magnets are located on the first outer ring. 
     
     
         17 . The electric motor of  claim 11 , wherein the at least one second bladed rotor includes a second opening to receive the second shaft, a second inner ring surrounding the second opening, and a second outer ring, wherein the second plurality of blades extend from the second inner ring to the second outer ring. 
     
     
         18 . The electric motor of  claim 17 , wherein the second plurality of magnets are located on the second outer ring. 
     
     
         19 . The electric motor of  claim 11 , further comprising a ducted fan connected to the first shaft within the air inlet, wherein rotation of the first shaft is utilized to rotate the ducted fan to route some of the air received via the air inlet to the ducts. 
     
     
         20 . The electric motor of  claim 11 , utilized in an aircraft.